Movably mounted auxiliary vanes for rotating combustion chamber



March 14, 195o 2,500,537

R. H. GODDARD MOVABLY MOUNTED AUXILIARY VANES FOR ROTATING COMBUSTIONCHAMBERS Filed May 7, 1947 lllllllllll Illll A C' N' Iii; I I r z l l Il{I- 7/ Patented Mar. 14, 1950 MOVABLY MOUNTED AUXILIABY VANS FORBOTATING COMBUSTION CHAMBER Robert H. Goddard, deceased, late ofAnnapolis, Md.,by Esther C. Goddard, executrix, Worcester, Mass.,assignor of one-half to The Daniel and Florence Guggenheim Foundation,New York, N. Y., a corporation of New York Application May 7, 1947,Serial No. 746,612

(Ci.v iiD-35.6)

3 Claims.

This invention relates to combustion chambers as used in propulsionapparatus, and relates more particularly to combustion chambers whichare mounted for rotation in ilight.

It is an important object of the present invention to provide auxiliarymeans for starting rotation of the combustion chamber, and means forcutting out the auxiliary starting means when rotation is under way.

A further object is to provide auxiliary means utilizing dischargedcombustion gases to increase the speed of rotation of the chamber untila predetermined speed is reached, and therefore automaticallyjbecominginoperative.

Another feature of the invention relates to the provision of means tocounteract the gyroscopic effect of the rotating combustion chamber.

The invention further relates to arrangements and combinations of partswhich will be hereinafter described and more particularly pointed out inthe appended claims.

Preferred forms of the invention are shown in the drawing, in which Fig.l is a side elevation of certain parts of a rotating combustion chamber,partly in section and embodying this invention;

Fig. 2 is an end view, looking in the direction of the arrow 2 in Fig.1, but with certain parts omitted for clearness;

Fig. 3 is a view similar to Fig. 1 but showing the auxiliary vanes inhigh-speed and inoperative position;

Fig. 4 is a partial perspective view showing auxiliary means forstarting rotation of the combustion chamber;

Fig. 5 is a sectional side elevation of a modied construction in whichboth the combustion chamber and the rocket craft rotate but in oppositedirections; and

Fig. 6 is a partial longitudinal section of the construction shown inFig. 5.

Referring to Figs. 1, 2 and 3, a combustion chamber C is shown which isprovided with the usual rearwardly extending nozzle N through which thecombustion gases are discharged. Spirally disposed vanes I0 are mountedin the nozzle N, which vanes are preferably hook-shaped as shown in endview in Fig. 2.

When the combustion chamber is in full operation and developing fullpower, the vanes I0 continuously rotate the chamber C at the desiredspeed, but the chamber is rather slow in picking up speed when iirststarted. Accordingly, auxiliary vanes 20 are provided which arepositioned rearward of the nozzle N and which are aligned with thenozzle opening when the chamber is at rest, as shown in Figs. 1 and 2.

The vanes 20 are curved to correspond with the curvature of the vanes i0and assist in building up rotational speed and in the same direction ofrotation. 'Ihe vanes 20 are mounted on iiat spring arms 22 which .extendthrough slots 24 in a casing 25 and which are firmly secured to thenozzle N, as by rivets 26.

The springs 22 are of such strength and thickness that the vanes 20 willbe swung outward by centrifugal force to the position shown in Fig. 3when the chamber C has been brought up to a desired speed of rotation.The vanes 20 are thereafter inoperative and the chamber continues torotate at the desired speed by the rotational eiect of the vanes i0 inthe nozzle N.

The casing 25 encloses the vanes 20 in all positions and reduces airresistance. A streamlined outer casing 30 may be added to further reduceair resistance, if the combustion chamber is not enclosed in the casingof a rocket craft R as shown in Fig. 4.

Auxiliary apparatus is also shown in Fig. 4 by which the combustionchamber C may be initially started to rotate from a position of rest.For this purpose, a small powder rocket or a compressed air nozzle d0 ismounted to discharge a uid at high speed against an annular series ofvanes 02 mounted on the outside of the chamber C. These vanes arepreferably curved as indicated, so that the uid is reversed indirection, and so that increased power is thus obtained therefrom.

The device 00 is intended for operation only to start rotation of thechamber, and it is desirable to discontinue the operative effect oi thedevice 40 as soon as the chamber C is rotating at the relatively lowspeed at which the vanes i0 and 20 can take over and continue.

The device 40 is accordingly pivoted at 44 and is provided with asolenoid plunger B5 extending through a solenoid coil 46. One terminalof the coil is grounded on the casing of the craft R by a wire 41, andthe other terminal of the coil is connected through a battery B to abrush or contact which continuously engages an insulated commutator ring5l connected by a wire 52 to a leaf spring 53 mounted on but insulatedfrom the combustion chamber C.

When rotation of the combustion chamber comes up to a predeterminedspeed, the spring 53 swings outward under centrifugal force and engagesa bracket 54 supported by and grounded on the chamber C. When thiscontact is made,

3 the solenoid circuit is completed and the device III is swung outwardas indicated by the arrow a, so that thestream of air, gas or vaporowing therefrom no longer engages the turbine blades I2. The productionof excessive rotative speed for the combustion chamber is thus avoided.

Under certain operating conditions, it may be necessary to neutralizethe gyroscopic effect of the rotating combustion chamber. For thispurpose the construction shown in Figs. 5 and 6 may be used. Acombustion chamber C is mounted in bearings 60 in a rocket craft R' andis provided with the usual nozzle N'. Spiral vanes 62 are provided inthe nozzle N', and thev combustion chamber is rapidly rotated therebywithin the craft R' as previously described.

In orderto neutralize the gyroscopic eect, provision is made to rotatethe rocket craft R and fuel tank T in the opposite direction to thechamber C and at a speed Just sufficient to neutralize the more rapidrotation of the chamber.

For this purpose, the rear end portion of the rocket craft casing isextended as indicated in Figs. 5 and 6 and is provided with a pluralityof short angularly disposed vanes 1l which are substantially in linewith the vanes 62 in the nozzle N' but which are disposed at a reverseangle. Consequently, the combustion gases discharged through the nozzleN' will engage the vanes 1l after leaving the nozzle and will rotate thecraft R in the opposite direction.

The neutralizing eiir'ect of such opposite rotation will be increased ifthe load of fuel in the tank T also partakes of this rotation, and forthis purpose longitudinally disposed baille plates 85 may be mounted inthe tank T but with clearance at eachend, so that all portions of thefuel may be accessible for use.

Provision is thus made fo'r initially starting the combustion chamber'inrotation, for continuing such rotation by the action of the combustiongases discharged from the rotating chamber, and for accelerating thebuilding up of a desired speed of rotation by auxiliary vanes whichbecome inoperative at a predetermined speed of rotation.

Having thus described the invention and the advantages thereof, it willbe understood that the invention is not to be limited to the detailsherein disclosed, otherwise than as set forth in the claims, but what isclaimed is:

1. In propulsion apparatus, a combustion chamber having an open rearwarddischarge nozzle, means to rotatably support said combustion chamber,spiral vanesin said nozzle with nozzle, means to rotatably support saidcombustion chamber, spiral vanes in said nozzle with which thedischarging combustion gases coact to rotate said chamber. and auxiliaryvanes mounted on and beyond the open rear end of said nozzle to provideadditional starting torque, and said auxiliary vanes being mounted tomove radially outward and out of the gas stream under centrifugal forceand to thereby become inoperative at a predetermined speed.

3. The combination in propulsion apparatus as set forth in claim 2, inwhich the auxiliary vanes are mounted on spring arms fixed to saidnozzle and which arms yield under centrifugal force and thereby permitsaid vanes to move outward when the predetermined speed is attained.

ESTHER C. GODDARD, I I

Eecutri of the Last Will and TestamentI of Robert H. Goddard, "Deceased,

REFERENCES CITED The following references are of record in the UNITEDSTATES PATENTS Goddard Feb. 26, 1946

